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公开(公告)号：US20240360788A1
公开(公告)日：2024-10-31
申请号：US18771005
申请日：2024-07-12
申请人： RTX CORPORATION
CPC分类号： F02C3/30 , F02C1/10 , F02C3/22 , F02C6/18 , F02C7/141 , F05D2220/323 , F05D2260/213
摘要： An aircraft propulsion system includes a core engine and a bottoming cycle where a working fluid is circulated within a closed circuit. A first heat exchanger is used to transfer heat from a portion of thermal energy from the exhaust gas flow to working fluid of the bottoming cycle. A fuel/working fluid heat exchanger provides the cryogenic fuel to cool the working fluid exhausted from a bottoming turbine and before a bottoming compressor.
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公开(公告)号：US20240309806A1
公开(公告)日：2024-09-19
申请号：US18120821
申请日：2023-03-13
发明人： Gregory Boardman
IPC分类号： F02C3/30
CPC分类号： F02C3/30 , F05D2220/32 , F05D2240/35 , F05D2270/08
摘要： An assembly is provided for a turbine engine. This assembly includes a combustor and an injection system. The combustor includes a combustion chamber. The injection system includes an injector. The injection system is configured to direct fluid and steam into the combustion chamber through the injector. The injection system is configured to modulate a flow of the fluid into the combustion chamber through the injector by regulating a flow of the steam into the combustion chamber through the injector.
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公开(公告)号：US12092023B1
公开(公告)日：2024-09-17
申请号：US18121503
申请日：2023-03-14
CPC分类号： F02C3/305 , F02C3/30 , F02C7/18 , F23R3/10 , F23R2900/03044
摘要： An assembly is provided for a turbine engine. This assembly includes a housing, a combustor and a steam system. The housing includes an air plenum. The combustor is disposed within the air plenum. The combustor includes a combustion chamber and a combustor wall between the combustion chamber and the air plenum. The steam system includes a steam injector arranged within the air plenum next to the combustor wall. The steam system is configured to inject steam out of the steam injector and into the air plenum to impinge against the combustor wall.
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公开(公告)号：US12078104B2
公开(公告)日：2024-09-03
申请号：US18317545
申请日：2023-05-15
CPC分类号： F02C7/1435 , F02C3/20 , F02C3/22 , F02C3/30 , F02C3/305 , F02C7/143 , F02C7/224 , F02C7/22 , F02C7/36
摘要： A propulsion system includes a core engine generating a high energy gas flow, a condenser configured to extract water from the high energy gas flow and an evaporator transforming the extracted water into a steam flow. The steam flow is injected into a core flow path of the core engine increase mass flow.
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公开(公告)号：US12078101B2
公开(公告)日：2024-09-03
申请号：US17605898
申请日：2020-04-10
CPC分类号： F02C3/305 , F02C9/28 , F05D2220/323 , F05D2220/329 , F05D2270/053 , F05D2270/16 , F05D2270/3062
摘要： A method for controlling a turbomachine including a temporary power-increasing device, the control method including a step wherein the flow rate of the coolant injected is adjusted as a function of the atmospheric pressure and/or of the ambient temperature and/or of at least one parameter such as the speed of rotation of a gas generator, the speed of rotation of a low-pressure turbine or of a power turbine, the gas pressure at the outlet of a compressor stage, the temperature at the inlet of the low-pressure turbine or of the power turbine, the engine torque, and/or the collective pitch of a helicopter rotor or the pitch of a propeller of a turboprop.
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公开(公告)号：US12065964B1
公开(公告)日：2024-08-20
申请号：US18302081
申请日：2023-04-18
发明人： Neil J. Terwilliger
CPC分类号： F02C3/34 , F02C3/30 , F02C6/20 , F02C7/141 , F02C7/1435 , F02C9/18 , F05D2260/212 , F05D2260/213
摘要： A turbine engine assembly includes a heat exchanger that is in thermal communication with an exhaust gas flow. A bypass passage is provided that is configured to selectively route at least a portion of the exhaust gas flow around the heat exchanger in response to a predefined engine operating condition.
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公开(公告)号：US12065963B2
公开(公告)日：2024-08-20
申请号：US18138481
申请日：2023-04-24
申请人： RTX Corporation
CPC分类号： F02C3/30 , F02C7/12 , F05D2220/323 , F05D2240/35 , F05D2260/207 , F05D2260/212 , F05D2260/213 , F05D2260/605
摘要： A method is provided during which an aircraft powerplant is provided. The aircraft powerplant includes a combustor and a water recovery system. The water recovery system includes a condenser and a reservoir. Fuel is combusted within the combustor to provide combustion products. Water is extracted from the combustion products using the condenser. The water recovery system is operated in one of a plurality of modes based on likelihood of contrail formation. The modes include a first mode and a second mode, where the water is collected within the reservoir during the first mode, and where the water passes through the water recovery system during the second mode.
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公开(公告)号：US12038177B1
公开(公告)日：2024-07-16
申请号：US18121436
申请日：2023-03-14
摘要： An assembly is provided for a turbine engine. This assembly includes a fuel injector assembly, and the fuel injector assembly includes a fuel passage, an air passage and a steam passage. The fuel injector assembly is configured to direct fuel out of the fuel passage along an axis into a volume as a fuel flow. The fuel injector assembly is configured to direct air out of the air passage along the axis into the volume as an air flow, where the air flow circumscribes the fuel flow. The fuel injector assembly is configured to direct steam out of the steam passage along the axis into the volume as a steam flow, where the steam flow circumscribes the fuel flow and provides a radial buffer between the fuel flow and the air flow.
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公开(公告)号：US20240200497A1
公开(公告)日：2024-06-20
申请号：US18592194
申请日：2024-02-29
CPC分类号： F02C7/224 , B64D37/32 , F02C3/22 , F02C3/30 , F05D2260/213 , F05D2260/607 , F05D2260/99
摘要： Methods and apparatus to produce hydrogen gas turbine propulsion are disclosed. An example apparatus to produce propulsion in a gas turbine engine includes a fluid line to transport hydrogen from a hydrogen supply and an inert gas from an inert gas supply to a gas turbine combustor. The apparatus also includes at least one heat exchanger coupled to the fluid line to heat the inert gas and the hydrogen in the fluid line.
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10.发明公开公开(公告)号：US20240200491A1
公开(公告)日：2024-06-20
申请号：US18407648
申请日：2024-01-09
申请人： RTX CORPORATION
发明人： Edward Thomas Rocco , Danbing Seto , Coy Bruce Wood , Liang Tang
CPC分类号： F02C3/30 , F02C3/22 , F02C7/185 , F05D2220/323 , F05D2260/211 , F05D2260/213 , F05D2260/2322 , F05D2260/607 , F05D2260/80 , F05D2270/3015
摘要： A propulsion system for an aircraft includes a hydrogen fuel system, a water recovery system and a water pressure and quantity monitoring system. The water recovery system uses a condenser to extract water from an exhaust gas flow. The water pressure and quantity monitoring system measures water pressures and quantities at various locations in the water recovery system to assess the health and efficiency of the water recovery/supply system and the propulsion system.
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